# TCDS A00009CH: Cirrus Design Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Cirrus Design Corporation
- Revision: 25
- Revised: December 26, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 8,724, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/dc/68/dc688b1226e75ceeb10371e2211e203b40a04f0656f6468d77b738b91dee3ddd
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID140348100520260127142917.0001
- Page: https://openairdocs.org/tcds/A00009CH

## Models (3)

As the data sheet lists them.

- SR22T
- SR22
- SR20

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No.  1 2 3 4 5 6 7 8 9 10  11  12  13  14  
Rev. No.  24 22  22  22  19  21  19  17  22  25 25 25 24  25  
 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A00009CH 
Revision 25 
Cirrus Design 
Corportation 
SR20 
SR22 
SR22T 
December 26, 2025 
 
TYPE CERTIFICATE DATA SHEET NO. A00009CH 
This data sheet, which is part of Type Certificate No. A00009CH, prescribes conditions and limitations under which the product 
for the which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder: Cirrus Design Corporation  
4515 Taylor Circle  
Duluth, MN 55811 
I - MODEL SR20, (NORMAL CATEGORY), APPROVED OCTOBER 23, 1998 
Engine 1. One (1) Continental Motors, Inc. IO-360-ES engine, Type Certificate Data Sheet (TCDS) E1CE 
 2. One (1) Lycoming Engines IO-390-C3B6 engine, Type Certificate Data Sheet (TCDS) E00006NY 
  
Fuel 100/100LL minimum grade aviation gasoline 
  
Engine Limits Continental Motors, Inc. IO-360-ES 
 Maximum Take-off 2700 RPM (200 hp) 
 Maximum Continuous Power  2700 RPM (200 hp) 
  
 Lycoming Engines IO-390-C3B6 
Maximum Take-off 2700 RPM (215 hp) 
Maximum Continuous Power  2700 RPM (215 hp) 
  
Propeller and  1. Hartzell Propeller Inc. P/N BHC-J2YF-1BF/F7694 (See Note 8) 
Propeller limits TCDS P37EA 
 Maximum Diameter: 76 inches 
 Minimum Diameter: 73 inches 
 Number of Blades: 2 
 Low Pitch: 14.6°+/-0.5° 
 High Pitch: 35.0°+/-1.0° 
 High Pitch: 35.0°+/-1.0° 
 Not to be operated above 24 inches of manifold pressure between 1900 and 2200 RPM. 
 Spinner: Hartzell P/N A-2295(P) NOTE: Spinner may be painted or polished. 
  
 2. Hartzell Propeller Inc. P/N PHC-J3YF-1MF/F7392-1 (See Note 8) 
 TCDS P36EA 
 Maximum Diameter: 74 inches 
 Minimum Diameter: 72 inches 
 Number of Blades: 3 
 Low Pitch: 14.1°+/-0.5° 
 High Pitch: 35.0°+/-1.0° 
 No operating limitations to 2800 RPM 
 Spinner: Hartzell P/N A-2295-1P 
  
 3. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7392-1 (See Note 8) 
 TCDS P36EA 
 Maximum Diameter: 74 inches 
 Minimum Diameter: 72 inches 
 Number of Blades: 3 
 Low Pitch: 13.9°+/-0.5° 
 High Pitch: 35.0°+/-1.0° 
 No operating limitations to 2800 RPM 
 Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished.

Page 2 of 14  A00009CH  
 
 4. Hartzell Propeller Inc. P/N HC-E3YR-1RF/F7392S-1 (See Note 9) 
TCDS P33EA 
Maximum Diameter: 74 inches 
Minimum Diameter: 73 inches 
Number of Blades: 3 
Low Pitch: 13.4°+/-0.5° 
High Pitch: 30.0°+/-1.0° 
No operating limitations to 2850 RPM 
Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 
  
 5. Hartzell Propeller Inc. P/N 3C1-R919A1/76C03-2 (See Note 9) 
TCDS P00016CH 
Maximum Diameter: 74 inches 
Minimum Diameter: 74 inches 
Number of Blades: 3 
Low Pitch: 11.9°+/-0.5° 
High Pitch: 30.0°+/-1.0° 
No operating limitations to 2700 RPM 
Spinner: Hartzell P/N 105890 NOTE: Spinner may be painted or polished. 
  
Airspeed 
Limits 
S/N 1005 thru 1147: 
Vne Never Exceed Speed 200 KIAS 
 Vno Maximum Structural Cruising Speed 165 KIAS 
 Vo (2900 lbs) Operating Maneuvering Speed 135 KIAS 
 Vo (2600 lbs) Operating Maneuvering Speed 126 KIAS 
 Vo (2200 lbs) Operating Maneuvering Speed 116 KIAS 
 Vfe Maximum Flap Extension Speed 100 KIAS 
 Vpd Maximum Parachute Deployment Speed 135 KIAS 
    
 S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is 
complied with:  
 Vne Never Exceed Speed 200 KIAS 
 Vno Maximum Structural Cruising Speed 165 KIAS 
 Vo (3000 lbs) Operating Maneuvering 131 KIAS 
 Vo (2600 lbs) Operating Maneuvering 122 KIAS 
 Vo (2300 lbs) Operating Maneuvering 114 KIAS 
 Vfe Maximum Flap Extension Speed 100 KIAS 
 Vpd Maximum Parachute Deployment Speed 135 KIAS 
    
 S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): 
 Vne Never Exceed Speed 200 KIAS 
 Vno Maximum Structural Cruising Speed 163 KIAS 
 Vo (3050 lbs) Operating Maneuvering 130 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 119 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   104 KIAS 
 Vpd Maximum Parachute Deployment Speed 133 KIAS 
    
 S/N 2220, 2339 and subsequent (See Note 9): 
 Vne Never Exceed Speed 201 KIAS 
 Vno Maximum Structural Cruising Speed 164 KIAS 
 Vo (3150 lbs) Operating Maneuvering 133 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 150 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   110 KIAS 
 Vpd Maximum Parachute Deployment Speed 133 KIAS 
    
C.G. Range S/N 1005 thru 1147: 
Forward Limits: 138.7 inches at 2110 lbs with a straight line taper to 141.0 inches at 2694 lbs, and 143.0 
inches at 2900 lbs. 
 
Aft Limits: 144.6 inches at 2110 lbs, with straight line taper to 147.4 inches at 2570 lbs, and to 147.9 inches at 
2745 lbs, and 148.2 inches at 2900 lbs.

Page 3 of 14  A00009CH  
 
 S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is 
complied with: 
Forward Limits: 138.7 inches at 2110 lbs with a straight line taper to 141.0 inches at 2694 lbs, and 144.1 
inches at 3000 lbs. 
 
Aft Limits: 144.6 inches at 2110 lbs, with straight line taper to 147.4 inches at 2570 lbs, and to 148.1 inches at 
2900 lbs, and 148.0 inches at 3000 lbs. 
  
 S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): 
 Forward Limits: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 140.7 
 inches at 3050 lbs 
  
 Aft Limits: 148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3050 lbs. 
  
 S/N 2220, 2339 and subsequent (See Note 9): 
Forward Limits: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 141.1 
inches at 3150 lbs 
 
Aft Limits: 148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3150 lbs. 
  
Empty Weight 
C.G. Range 
None 
  
Maximum 
Weights 
S/N 1005 thru 1147: 
Takeoff and Landing: 2900 lbs. 
  
 S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is 
complied with: 
Takeoff: 3000 lbs. 
Landing: 2900 lbs. 
Zero Fuel: 2900 lbs. 
  
 S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): 
 Takeoff and Landing: 3050 lbs. 
  
 S/N 2220, 2339 and subsequent (See Note 9): 
Takeoff and Landing: 3150 lbs. 
  
Minimum 
Crew 
One (1) Pilot 
  
Number of 
Seats 
S/N 1005 thru 2126: 
4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) 
  
 S/N 2127 thru 2219, and S/N 2221 thru 2338: 
 4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) 
  
 S/N 2220, 2339 and subsequent: 
4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) 
3 (2 at 143.5 inches aft of datum, 1 at 180 inches aft of datum) 
2 (2 at 143.5 inches aft of datum) 
  
Maximum 
Baggage: 
130 Lbs. at 208 inches 
  
Fuel Capacity 
Total: 
S/N 1005 thru 1877, 1879 thru 1885: 
60.5 gal at 153.75 inches 
Usable: 56 gal (See Note 1) 
  
 S/N 1878, 1886 and subsequent: 
58.5 gal at 154.9 inches 
Usable: 56 gal (See Note 1)

Page 4 of 14  A00009CH  
 
Oil Capacity S/N 1005 thru 2219, and S/N 2221 thru 2338 (See Note 8): 
 8 quarts at 76.2 inches 
  
 S/N 2220, 2339 and subsequent (See Note 9): 
7 quarts at 80.5 inches 
  
Maximum 
Operating 
Altitude 
The aircraft is limited to 17,500 ft MSL. 
  
Control Surface 
Movements 
Wing Flaps: Up 0°± 0.5° Down 50% 16°± 0.5°   Down 100% 32°± 0.5° 
Aileron: Up 12.5° ± 1.0° Down 12.5° ±1.0°  
 Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°  
 Elevator Trim: Up 17.0°  Minimum Down 10.5° ± 1.0°  
 Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°  
     
Additional 
Limitations: 
Airframe life limit:  12,000 flight hours 
 
  
Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing 
List”, Document No. 13750, or other FAA approved data.  NOTE:  Document No. 12609 is the predecessor 
document to Document No. 13750. 
  
Serial Nos. 
Eligible 
1005 and on 
II - MODEL SR22, NORMAL CATEGORY, APPROVED NOVEMBER 30, 2000 
Engine One (1) Continental Motors, Inc. IO-550-N engine, Type Certificate Data Sheet  E3SO 
  
Fuel 100/100LL minimum grade aviation gasoline 
  
Engine Limits Maximum Take-off 2700 RPM (310 hp) 
Maximum Continuous Power 2700 RPM (310 hp) 
  
Propeller and 
Propeller limits 
1. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7694 or F7694B 
TCDS P36EA  Hartzell   
Maximum Diameter: 78 inches 
Minimum Diameter: 76 inches 
Number of Blades: 3 
Low Pitch: 14.1°+/-0.5° 
High Pitch: 35.0°+/-1.0° 
No operating limitations to 2700 RPM 
Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 
  
 2. McCauley Propeller Systems P/N D3A34C443/78CYA-0 
TCDS P47GL  McCauley 
Maximum Diameter: 78 inches 
Minimum Diameter: 76 inches 
Number of Blades: 3 
Low Pitch: 11.8°+/-0.5° at 30” station 
High Pitch: 31.5° at 30” station 
No operating limitations to 2700 RPM 
Spinner: McCauley D-7779-1 (Polished) or D-7779-2 (Satin)

Page 5 of 14  A00009CH  
 
 3. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7693DF or F7693DFB 
TCDS P36EA  Hartzell   
Maximum Diameter: 78 inches 
Minimum Diameter: 76 inches 
Number of Blades: 3 
Low Pitch: 13.9°+/-0.5° 
High Pitch: 40.0°+/-1.0° 
No operating limitations to 2700 RPM 
Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 
  
 4. Hartzell Propeller Inc. P/N PHC-J3YF-1N/N7605 or N7605B 
TCDS P36EA  Hartzell   
Maximum Diameter: 78 inches 
Minimum Diameter: 78 inches 
Number of Blades: 3 
Low Pitch: 12.2°+/-0.5° 
High Pitch: 35.0°+/-1.0° 
No operating limitations to 2700 RPM  
Spinner: Hartzell P/N A-2295-11(P) NOTE: Spinner may be painted or polished. 
  
 5. Hartzell Propeller Inc. P/N PHC-J3Y1F-1N/N7605, N7605B, N7605C or N7605CB 
TCDS P36EA  Hartzell   
Maximum Diameter: 78 inches 
Minimum Diameter: 78 inches 
Number of Blades: 3 
Low Pitch: 12.2°+/-0.5° 
High Pitch: 35.0°+/-1.0° 
No operating limitations to 2700 RPM when using type design throttle-propeller controls 
Spinner: Hartzell P/N 102870() or A-2295-11() NOTE: () indicates various finish options. 
  
 6. MT-Propeller Entwicklung GmbH P/N MTV-9-D/198-52 
TCDS P24NE MT-Propeller   
Maximum Diameter: 78 inches 
Minimum Diameter: 76 inches 
Number of Blades: 3 
Low Pitch: 12.5°+/-0.2° 
High Pitch: 38.0°+/-1.0° 
No operating limitations to 2700 RPM  
Spinner: MT-Propeller P/N P-187 NOTE: Spinner may be painted or polished. 
  
Airspeed 
Limits 
S/N 0002 thru 3914: 
Vne Never Exceed Speed 204 KIAS 
 Vno Maximum Structural Cruising Speed 180 KIAS 
 Vo (3400 lbs) Operating Maneuvering 133 KIAS 
 Vo (2900 lbs) Operating Maneuvering 124 KIAS 
 Vo (2400 lbs) Operating Maneuvering 112 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 119 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   104 KIAS 
 Vpd Maximum Parachute Deployment Speed 133 KIAS 
    
 S/N 3915 and subsequent: 
 Vne Never Exceed Speed 208 KIAS 
 Vno Maximum Structural Cruising Speed 179 KIAS 
 Vo (3600 lbs) Operating Maneuvering 140 KIAS 
 Vo (3400 lbs) Operating Maneuvering 133 KIAS 
 Vo (2900 lbs) Operating Maneuvering 124 KIAS 
 Vo (2400 lbs) Operating Maneuvering 112 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 150 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   110 KIAS 
 Vpd Maximum Parachute Deployment Speed 140 KIAS 
    
C.G. Range S/N 0002 thru 3914: 
Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 142.3 inches at 
3400 lbs.  (See Note 6) 
 
Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3400 lbs.

Page 6 of 14  A00009CH  
 
  
 S/N 3915 and subsequent: 
Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 143.2 inches at 
3600 lbs. 
 
Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3600 lbs 
  
Empty Weight 
C.G. Range 
None 
  
Maximum 
Weights 
S/N 0002 thru 3914: 
3400 lbs 
  
 S/N 3915 and subsequent: 
Takeoff and Landing:  3600 lbs 
Zero Fuel:  3400 lbs 
  
Minimum 
Crew 
One (1) Pilot 
  
Number of 
Seats 
S/N 0002 thru 3827: 
4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) 
  
 S/N 3828 and subsequent: 
4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) 
  
Maximum 
Baggage 
130 Lbs. at 208 inches 
  
Fuel Capacity 
Total: 
S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437: 
84 gallon at 154.9 inches 
Usable: 81 gallon (See Note 1) 
  
 S/N 2334, 2420, 2438 and subsequent: 
94.5 gallon at 154.9 inches 
Usable: 92.0 gallon (See Note 1) 
  
Oil Capacity 8 quarts at 77.1 inches 
  
Maximum 
Operating 
Altitude 
The aircraft is limited to 17,500 ft MSL. 
  
Control Surface 
Movements 
S/N 0002 thru 3914: 
Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 32° ±0.5° 
 Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0°  
 Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°  
 Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°  
 Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°  
     
 S/N 3915 and subsequent: 
 Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 35.5° ±0.5° 
 Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0°  
 Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°  
 Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°  
 Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°  
     
Additional 
Limitations: 
Airframe life limit:  12,000 flight hours 
  
Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing 
List”, Document No. 13750, or other FAA approved data. 
  
Serial Nos. 
Eligible 
Eligible 0001 and on.

Page 7 of 14  A00009CH  
 
III - MODEL SR22T, NORMAL CATEGORY, APPROVED FEBRUARY 10, 2010 
Engine One (1) Continental Motors, Inc. TSIO-550-K engine, Type Certificate Data Sheet  E5SO 
  
Fuel 100/100LL minimum grade aviation gasoline 
  
Engine Limits Maximum Take-off 2500 RPM (315 hp) 
Maximum Continuous Power 2500 RPM (315 hp) 
  
Propeller and 
Propeller limits 
Hartzell Propeller Inc. P/N PHC-J3Y1F-1N/N7605, N7605B, N7605C or N7605CB 
TCDS P36EA  Hartzell   
Maximum Diameter: 78 inches 
Minimum Diameter: 78 inches 
Number of Blades: 3 
Low Pitch: 12.2°+/-0.5° 
High Pitch: 35.0°+/-1.0° 
No operating limitations to 2700 RPM 
Spinner: Hartzell P/N 102870() or A-2295-11() NOTE: () indicates various finish options. 
  
Airspeed 
Limits 
S/N 0001 thru 0441: 
Vne Never Exceed Speed 204 KCAS from S/L to 17,500 ft MSL linearly 
reducing from 204 KCAS @ 17,500 ft to 173 
KCAS @ 25,000 ft 
 Vno Maximum Structural Cruising Speed 180 KCAS from S/L to 17,500 ft MSL linearly 
reducing from 180 KCAS @ 17,500 ft to 153 
KCAS @ 25,000 ft 
 Vo (3400 lbs) Operating Maneuvering 133 KIAS 
 Vo (2900 lbs) Operating Maneuvering 124 KIAS 
 Vo (2400 lbs) Operating Maneuvering 112 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 119 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   104 KIAS 
 Vpd Maximum Parachute Deployment Speed 133 KIAS 
    
 S/N 0442 and subsequent: 
 Vne Never Exceed Speed 208 KCAS from S/L to 17,500 ft MSL linearly 
reducing from 208 KCAS @ 17,500 ft to 178 
KCAS @ 25,000 ft 
 Vno Maximum Structural Cruising Speed 179 KCAS from S/L to 17,500 ft MSL linearly 
reducing from 179 KCAS @ 17,500 ft to 152 
KCAS @ 25,000 ft 
 Vo (3600 lbs) Operating Maneuvering 140 KIAS 
 Vo (3400 lbs) Operating Maneuvering 133 KIAS 
 Vo (2900 lbs) Operating Maneuvering 124 KIAS 
 Vo (2400 lbs) Operating Maneuvering 112 KIAS 
 Vfe Maximum Flap Extension Speed (50%) 150 KIAS 
 Vfe Maximum Flap Extension Speed (100%)   110 KIAS 
 Vpd Maximum Parachute Deployment Speed 140 KIAS 
    
C.G. Range S/N 0001 thru 0441: 
Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 142.3 inches at 
3400 lbs.  (See Note 6) 
 
Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3400 lbs. 
  
 S/N 0442 and subsequent: 
Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 143.2 inches at 
3600 lbs. 
 
Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3600 lbs 
  
Empty Weight 
C.G. Range 
None 
  
Maximum 
Weights 
S/N 0001 thru 0441: 
3400 lbs

Page 8 of 14  A00009CH  
 
 S/N 0442 and subsequent: 
Takeoff and Landing: 3600 lbs 
Zero Fuel:  3400 lbs 
  
Minimum 
Crew 
One (1) Pilot 
  
Number of 
Seats 
S/N 0001 thru 0250, and 0252 thru 0267: 
4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) 
  
 S/N 0251, 0268 and subsequent: 
4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) 
  
Maximum 
Baggage 
130 Lbs. at 208 inches 
  
Fuel Capacity 
Total: 
94.5 gallon at 154.9 inches 
Usable: 92.0 gallon (See Note 1) 
  
Oil Capacity 8 quarts at 77.1 inches 
  
Maximum 
Operating 
Altitude 
The aircraft is limited to 25,000 ft MSL. 
  
Control Surface 
Movements 
S/N 0001 thru 0441: 
Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 32° ±0.5° 
 Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0°  
 Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°  
 Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°  
 Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°  
     
 S/N 0442 and subsequent: 
 Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 35.5° ±0.5° 
 Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0°  
 Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°  
 Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°  
 Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°  
     
Additional 
Limitations: 
Airframe life limit:  12,000 flight hours 
  
Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing 
List”, Document No. 13750, or other FAA approved data. 
  
Serial Nos. 
Eligible 
Eligible 0001 and on

Page 9 of 14  A00009CH  
 
DATA PERTINENT TO ALL MODELS 
Reference Datum 100 inches in front of the forward face of firewall bulkhead 
 
Leveling Means Door sill and leveling points as defined in AFM 
 
Certification Basis Model SR20: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as 
amended by 23-1 thru 23-47, except as follows: 
 
 14 CFR 23.573, 23.575, 23.611, 23.657, 23.673 thru Amendment 23-48;  
 14 CFR 23.783, 23.785, 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 
23.1329, 23.1361, 23.1383, 23.1401, 23.1431, 23.1435 thru Amendment 23-49; 
 14 CFR 23.3, 23.25, 23.143, 23.145, 23.155, 23.1325, 23.1521, 23.1543, 23.1555, 23.1559, 
23.1567, 23.1583, 23.1585, 23.1589 thru Amendment 23-50; 
 14 CFR 23.777, 23.779, 23.901, 23.907, 23.955, 23.959, 23.963, 23.965, 23.973, 23.975, 
23.1041, 23.1091, 23.1093, 23.1107, 23.1121, 23.1141, 23.1143, 23.1181, 23.1191, 23.1337 thru 
Amendment 23-51; 
 14 CFR 23.1305 thru Amendment 23-52 
 
 14 CFR Part 36 dated December 1, 1969 as amended by 36-1 thru 36-21. 
 
 In addition to the certification basis stated above, for SR20 S/N 1423 thru 1877 and SR20 serials 
1879 and subsequent the certification basis is amended to include the following regulations at 
the amendment levels stated for the SR20 Fuselage Redesign (G2 marketing designation): 
 
 14 CFR 23.561, 23.607, 23.629 thru Amendment 23-48. 
 14 CFR 23.853 thru Amendment 23-49. 
 14 CFR 23.161, 23.177, 23.201, 23.203, 23.233, 23.1581 thru Amendment 23-50. 
 14 CFR 23.925, 23.1043, 23.1047, 23.1183 thru Amendment 23-51. 
 14 CFR 23.901 thru Amendment 23-53. 
 
 In addition to the certification basis stated in the paragraphs above, for SR20 S/N 1878, 1886 
and subsequent the certification basis is amended to include the following regulations at the 
amendment levels stated for SR20 Wing Redesign (G3 marketing designation): 
 
 14 CFR 23.473, 23.499, 23.725, 23.865 thru Amendment 23-48. 
 14 CFR 23.677, 23.723, 23.735, 23.1351, 23.1353, 23.1359, 23.1365 thru 23-49. 
 14 CFR 23.45, 23.49, 23.51, 23.53, 23.63, 23.71, 23.75, 23.77, 23.147, 23.157, 23.175, 23.1511,  
 23.1553, 23.1563 thru Amendment 23-50. 
  
 For aircraft equipped with Garmin G1000 avionics or Garmin G1000 avionics with Garmin 
GFC-700 autopilot system, the certification basis, for installation specific items only, is amended 
to include the following regulation at the amendment level stated: (Effective S/N 2016 thru S/N 
2219 and S/N 2221 thru 2338): 
 
 14 CFR 23.1308 thru Amendment 23-57. 
 
 For aircraft equipped with Garmin G1000 NXi avionics or Garmin G1000 NXi avionics with 
Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is 
amended to include the following regulation at the amendment level stated (Effective S/N 2220, 
2339 and subsequent): 
 
 14 CFR 23.207 thru Amendment 23-50. 
14 CFR 23.1308 thru Amendment 23-57. 
14 CFR 23.1306 thru Amendment 23-61 
 
 For aircraft equipped with Lycoming Engines IO-390-C3B6 the certification basis is amended to 
include the following regulations at the amendment levels stated (Effective S/N 2220, 2339 and 
subsequent): 
 
 14 CFR 23.572 thru Amendment 23-48. 
14 CFR 23.697, 23.701, 23.787, 23.865, thru Amendment 23-49. 
14 CFR 23.33, 23.65, 23.69, 23.73, 23.153, 23.207, 23.235, 23.562, 23.1545, 23.1587 thru 
Amendment 23-50. 
14 CFR 23.925, 23.1043, 23.1047, 23.1183 thru Amendment 51. 
14 CFR 23.903 thru Amendment 23-54.

Page 10  of 14  A00009CH  
 
 14 CFR 23.905, 23.907 thru Amendment 23-59. 
14 CFR 23.1308 thru  Amendment 23-57. 
14 CFR 23.1306 thru Amendment 23-61. 
 
 14 CFR 36 dated December 1, 1969 as amended by 36-1 thru 36-30. 
 
The aircraft certification basis is amended to include the following regulation at the amendment 
level stated (Effective S/N 2650 and subsequent):  (Note:  The amended certification basis 
allows for the optional removal of the wet compass.)   
 
14 CFR 23.1303 thru Amendment 23-62 
 
 
The aircraft certification basis is amended (effective S/N 9750 and subsequent) to include only : 
 
14 CFR 23.2610 (a)(c) thru Amendment 23-64 effective S/N 9750 and subsequent 
 
14 CFR 23.853, 23.1311 and 23.1555 thru Amendment 23-62 effective S/N 9750 and 
subsequent  
 
For aircraft with a Lithium-ion Battery 14 CFR 23.2505, 23.2510 (a)(b)(c), 23.2525 (a)(b)(c), 
Amendment 23-64 with MOC per Issue Paper included with cert project. 
 
For aircraft equipped with A337 Halotron BrX fire extinguisher, the aircraft certification basis, 
for installation specific items only, is amended to include the following regulation at the 
amendment levels stated: (Effective S/N 11118 and subsequent): 
 
23.2325(f) (23-64); 
 
  
 Model SR22: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as 
amended by 23-1 thru 23-53, except as follows: 
 
 14 CFR 23.301 thru Amendment 23-42 
 14 CFR 23.855, 23.1326, 23.1359, not applicable 
 
 14 CFR Part 36 dated December 1, 1969, as amended by 36-1 thru 36-22 
 
 For aircraft equipped with Garmin G1000 avionics or Garmin G1000 avionics with Garmin 
GFC-700 autopilot system, the certification basis, for installation specific items only, is amended 
to include the following regulation at the amendment level stated: (Effective S/N 2979, 2992, 
3002 and subsequent): 
 
 14 CFR 23.1308 thru Amendment 23-57. 
 
 For aircraft equipped with Garmin G1000 NXi avionics or Garmin G1000 NXi avionics with the 
Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is 
amended to include the following regulation at the amendment level stated: (Effective S/N 4433 
and subsequent): 
 
 14 CFR 23.1308 thru Amendment 23-57. 
14 CFR 23.1306 thru Amendment 23-61. 
 
 For aircraft equipped for optional Flight Into Known Icing operation, the certification basis, for 
installation specific items only, is amended to include the following regulation at the amendment 
level stated: (Effective S/N 3003, 3310, 3326, 3403 and subsequent), 
 
 14 CFR 23.1326, 23.1359 thru Amendment 23-49. 
 14 CFR 23.1308 thru Amendment 23-57. 
 
 For aircraft with 3600 lb max takeoff and landing weight limitation, the certification basis, for 
installation specific items only, is amended to include the following regulation at the amendment 
level stated:  (Effective S/N 3915 and subsequent): 
 
 14 CFR 23.1308 thru Amendment 23-57.

Page 11  of 14  A00009CH  
 
 14 CFR Part 36 thru Amendment 36-28. 
 
 For aircraft equipped with Special Missions provisions (ref. AFM supplement 13772-157), the 
certification basis, for installation specific items only, is amended to include the following 
regulation at the amendment level stated: 
 
 14 CFR Part 36 thru Amendment 36-30. 
 
 
The aircraft certification basis is amended to include the following regulation at the amendment 
level stated (Effective S/N 4993 and subsequent):  (Note:  The amended certification basis 
allows for the optional removal of the wet compass.)   
 
14 CFR 23.1303 thru Amendment 23-62 
 
The aircraft certification basis is amended (effective S/N 9750 and subsequent) to include only : 
 
14 CFR 23.2610 (a)(c) thru Amendment 23-64 effective S/N 9750 and subsequent 
 
14 CFR 23.853, 23.1311 and 23.1555 thru Amendment 23-62 effective S/N 9750 and 
subsequent  
 
For aircraft with a Lithium-ion Battery 14 CFR 23.2505, 23.2510 (a)(b)(c), 23.2525 (a)(b)(c), 
Amendment 23-64 with MOC per Issue Paper included with cert project. 
 
For aircraft equipped with A337 Halotron BrX fire extinguisher, the aircraft certification basis, 
for installation specific items only, is amended to include the following regulation at the 
amendment levels stated: (Effective S/N 11118 and subsequent): 
 
23.2325(f) (23-64); 
 
 Model SR22T: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as 
amended by 23-1 thru 23-59, except as follows: 
 
 14 CFR 23.301 thru Amendment 23-42 
 
 14 CFR Part 36 dated December 1, 1969, as amended by 36-1 thru 36-28 
 
 For aircraft equipped with Special Missions provisions (ref. AFM supplement 13772-157), the 
certification basis, for installation specific items only, is amended to include the following 
regulation at the amendment level stated: 
 
 14 CFR Part 36 thru Amendment 36-30. 
 
 For aircraft equipped with Garmin G1000 NXi avionics or Garmin G1000 NXi avionics with the 
Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is 
amended to include the following regulation at the amendment level stated: (Effective S/N 1473 
and subsequent), 
 
 14 CFR 23.1308 thru Amendment 23-57. 
14 CFR 23.1306 thru Amendment 23-61. 
 
 
The aircraft certification basis is amended to include the following regulation at the amendment 
level stated (Effective S/N 2238 and subsequent):  (Note:  The amended certification basis 
allows for the optional removal of the wet compass.)   
 
14 CFR 23.1303 thru Amendment 23-62 
 
 
The aircraft certification basis is amended (effective S/N 9750 and subsequent) to include only : 
 
14 CFR 23.2610 (a)(c) thru Amendment 23-64 effective S/N 9750 and subsequent 
 
14 CFR 23.853, 23.1311 and 23.1555 thru Amendment 23-62 effective S/N 9750 and 
subsequent

Page 12  of 14  A00009CH  
 
 
For aircraft with a Lithium-ion Battery 14 CFR 23.2505, 23.2510 (a)(b)(c), 23.2525 (a)(b)(c), 
Amendment 23-64 with MOC per Issue Paper included with cert project. 
 
For aircraft equipped with A337 Halotron BrX fire extinguisher, the aircraft certification basis, 
for installation specific items only, is amended to include the following regulation at the 
amendment levels stated: (Effective S/N 11118 and subsequent): 
 
23.2325(f) (23-64); 
 
Equivalent Level 
of Safety (ELOS) 
Findings 
ACE-96-5 for 14 CFR Section (§) 23.221 (Spinning); Refer to FAA Memorandum dated June 10, 1998 
for models SR20, SR22. 
 
ACE-96-5A for 14 CFR § 23.221 (Spinning); Refer to FAA Memorandum dated February 02, 2010 for 
model SR22T. 
 
 ACE-01-01 for 14 CFR § 23.1143(g) (Engine Controls) and § 23.1147(b) (Mixture Controls); Refer to 
FAA Memorandum dated February 14, 2001 for model SR20. 
 
 ACE-00-09 for 14 CFR § 23.1143(g) (Engine Controls) and § 23.1147(b) (Mixture Controls); Refer to 
FAA Memorandum dated September 11, 2000 for model SR22. 
 
 ACE-00-09A for 14 CFR § 23.1143(g) (Engine Controls) and § 23.1147(b) (Mixture Controls); Refer to 
FAA Memorandum dated February 02, 2010 for model SR22T. 
 
 ACE-08-05 for 14 CFR § 23.777(d) (Cockpit Controls) and § 23.781(b) (Cockpit control knob shape); 
Refer to FAA Memorandum dated April 11, 2008 for models SR20, SR22. (effective with optional 
Garmin G1000 avionics installation, see certification basis above). 
 
 ACE-08-05A for 14 CFR § 23.777(d) (Cockpit Controls) and § 23.781(b) (Cockpit control knob shape); 
Refer to FAA Memorandum dated February 02, 2010 for model SR22T (all serials). 
 
 ACE-09-06 for 14 CFR § 23.1326(b)(1) (Pitot heat indication systems); for Flight Into Known Icing 
equipped airplanes only (Effective S/N 3003, 3310, 3326, 3403 and subsequent); Refer to FAA 
Memorandum dated April  20, 2009 for model SR22. 
 
 ACE-09-06A for 14 CFR § 23.1326(b)(1) (Pitot heat indication systems); Refer to FAA Memorandum 
dated February 02, 2010 for model SR22T (all serials). 
 
 ACE-10-08 for 14 CFR § 23.1091(b)(4) (Alternate air door override means); Refer to FAA 
Memorandum dated February 02, 2010 for model SR22T (all serials). 
 
Special Conditions 23-ACE-88 for ballistic parachute, for models SR20, SR22, SR22T. 
 
 23-134-SC for protection of systems for High Intensity Radiated Fields (HIRF), for models SR20, 
SR22. 
 
 23-163-SC for inflatable restraint system.  Addition to the certification basis model SR20 effective S/N 
1541 and subsequent; model SR22 S/N 1500, 1520 and subsequent; model SR22T (all serials). 
 
Exemptions Exemption No. 9849 to 14 CFR § 23.1419(a) for Flight Into Known Icing operations only on model 
SR22 (Effective S/N 3003, 3310, 3326, 3403 and subsequent). Exemption allows for a higher stall 
speed than that required by 14 CFR § 23.49(c) & (d) when operating in icing conditions.   
 
 Exemption No. 9993 to 14 CFR § 23.1419(a) for Flight Into Known Icing operations only on model 
SR22T (Effective S/N 0001 and on). Exemption allows for a higher stall speed than that required by 14 
CFR § 23.49(c) & (d) when operating in icing conditions.   
 
Production Basis TC Holder: Cirrus Design Corporation headquartered in Duluth, Minnesota. Production Certificate 
338CE issued June 12, 2000 
 
Licensee: AVIC General Huanan Aircraft Industry Co., Ltd located in the People’s Republic of China 
(PRC). Production Certificate No. PC0040A-ZN. Model effectivity includes all models and serial 
numbers with unique serial number ending in “H”.

Page 13  of 14  A00009CH  
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See 
Certification Basis) must be installed in the airplane for airworthiness certification. 
 
 In addition to the above required equipment, the following equipment are also required: 
 
 The latest FAA approved Revision of the “PILOT’S OPERATING HANDBOOK AND FAA 
APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS SR20”, Document No. 11934-001 for 
aircraft serials 1005 thru 1147 with 2900 pound TOGW, Document No. 11934-002 for aircraft serials 
1005 thru 1147 with 3000 pound TOGW and aircraft serials 1148 thru 1267, Document No. 11934-003 
for aircraft serials 1268 and subsequent with Analog or Avidyne Avionics System, Document No. 
11934-004 for aircraft serials 2016 and subsequent with Cirrus Perspective Avionics Suite, or 
Document No. 11934-005 for aircraft serials 2220, 2339 and subsequent with Cirrus Perspective+ 
Avionics System, and Document No.  AFM 44763-001 for aircraft serials 9750 and subsequent. (See 
Note 7) 
 
 
 The latest FAA approved Revision of the “PILOT’S OPERATING HANDBOOK AND FAA 
APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS SR22”, Document No. 13772-001 for 
aircraft serials 0002 thru 3025, Document No. 13772-002 for aircraft serials 2979, 2992, 3002 thru 
3914, or Document No. 13772-004 for aircraft serials 3915 thru 4434, or Document No. 13772-006 for 
aircraft serials 4435 thru 9749, and Document No.  AFM 44765-001 for aircraft serials 9750 and 
subsequent. (See Note 7) 
 
 The latest FAA approved Revision of the “PILOT’S OPERATING HANDBOOK AND FAA 
APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS SR22T”, Document No. 13772-003 for 
aircraft serials 0001 thru 0441, or Document No. 13772-005 for aircraft serials 0442 and subsequent, or 
Document No. 13772-007 for aircraft serials 1473, and Document No.  AFM 44767-001 for aircraft 
serials 9750 and subsequent. (See Note 7) 
 
Note 1. A current weight and balance report including list of equipment included in the certificated empty 
weight, and loading instructions when necessary must be provided for each aircraft at the time of 
original certification. The certificated empty weight and loading corresponding center of gravity 
location must include unusable fuel of: 
27 lb. at (+153.8 inches) for model SR20 S/N 1005 thru 1877, 1879 thru 1885. 
18 lb at (+154.9 inches) for model SR22 S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437. 
15 lb at (+154.9 inches) for models SR22 S/N 2334, 2420, 2438 and subsequent; SR20 S/N 1878, 1886 
and subsequent; and SR22T for S/N 0001 and subsequent. 
 
Note 2. All placards specified in the latest FAA approved revisions of the following documents must be 
displayed in the airplane in the appropriate locations: 
"PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 
FOR THE CIRRUS SR20", document numbers 11934-001, 11934-002, 11934-003, 11934-004, or 
11934-005. 
“PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 
FOR THE CIRRUS SR22" document numbers 13772-001, 13772-002, 13772-004, or 13772-006. 
"PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 
FOR THE CIRRUS SR22T" document number 13772-003, 13772-005, or 13772-007. 
 
Note 3. FAA approved Airworthiness Limitations are included in Section 4 of the Airplane Maintenance 
Manual (AMM) Document No. 12137-001 for model SR20 aircraft serials 1005 thru 2219, and 2221 
thru 2338 or  
Document No. 12137-002 for model SR20 serials 2220, 2339 and subsequent, and Document No. 
13773-001 for model SR22 aircraft serials 0002 thru 4432 and model SR22T aircraft serials 0001 thru 
1472 or Document No. 13773-002 for model SR22 aircraft serials 4433 and subsequent and model 
SR22T aircraft serials 1473 and subsequent. 
 
Note 4. Exterior colors are limited to those specified in the latest FAA accepted revision of the Airplane 
Maintenance Manual (AMM) Document No. 12137-001 for model SR20 aircraft serials 1005 thru 2219 
and 2221 thru 2338 or Document No. 12137-002 for model SR20 serials 2220, 2339 and subsequent, 
and Document No. 13773-001 for model SR22 aircraft serials 0002 thru 4432 and model SR22T aircraft 
serials 0001 thru 1472 or Document No. 13773-002 for model SR22 aircraft serials 4433 and 
subsequent and model SR22T aircraft serials 1473 and subsequent.

Page 14  of 14  A00009CH  
 
Note 6. 
 
 
Note 7. 
 
For Model SR22 S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437 a maximum landing weight 
exists along the line between 141.4 inches at 3210 lbs and 142.7 inches at 3400 lbs. 
 
The Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (POH) may be installed in 
the airplane in hardcopy format or on a portable device in electronic format in accordance with the 
limitations in the POH.  The electronic format has the same base and dash number as the hardcopy 
format and includes “ePOH” after the dash number. 
 
Note 8. For aircraft equipped with Teledyne Continental IO-360-ES. 
 
Note 9. For aircraft equipped with Lycoming Engines IO-390-C3B6. 
 
-- END --
```

## ADs (22, in force first)

- [AD 2024-24-11](https://openairdocs.org/ad/2024-24-11): Power Lever · Cirrus Design SR20, SR22 and SR22T. Effective Dec 23, 2024
- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023
- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2012-01-11](https://openairdocs.org/ad/2012-01-11): Engine Air Intake · Cirrus Design SR22T. Effective Feb 29, 2012
- [AD 2009-26-01](https://openairdocs.org/ad/2009-26-01): Ice and Rain protection · Cirrus Design SR22. Effective Dec 21, 2009
- [AD 2009-05-05](https://openairdocs.org/ad/2009-05-05): Primary Flight Displays · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 3, 2009
- [AD 2008-14-13](https://openairdocs.org/ad/2008-14-13): Upper door hinge · Cirrus Design SR20 and SR22. Effective Aug 14, 2008
- [AD 2008-11-18](https://openairdocs.org/ad/2008-11-18): Heat exchanger · Cirrus Design SR20. Effective Jul 7, 2008
- [AD 2008-03-16](https://openairdocs.org/ad/2008-03-16): Rudder, aileron, and rudder-aileron interconnect rigging · Cirrus Design SR20 and SR22. Effective Mar 11, 2008
- [AD 2007-24-13](https://openairdocs.org/ad/2007-24-13): Install a drain hole in the left and right outboard wing tips · Cirrus Design SR22. Effective Dec 4, 2007
- [AD 2007-14-03](https://openairdocs.org/ad/2007-14-03): Cirrus Airplane Parachute System (CAPS) · Cirrus Design SR20 and SR22. Effective Aug 16, 2007
- [AD 2006-21-03](https://openairdocs.org/ad/2006-21-03): Brake caliper piston O-ring seals · Cirrus Design SR20 and SR22. Effective Nov 17, 2006
- [AD 2006-19-10](https://openairdocs.org/ad/2006-19-10): Adjust crew seat break-over bolts · Cirrus Design SR20 and SR22. Effective Oct 24, 2006
- [AD 2006-07-06](https://openairdocs.org/ad/2006-07-06): Wire harness · Cirrus Design SR20 and SR22. Effective May 11, 2006
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2002-24-08](https://openairdocs.org/ad/2002-24-08): Cable clamp · Cirrus Design SR20 and SR22. Effective Jan 24, 2003
- [AD 2002-21-02](https://openairdocs.org/ad/2002-21-02): Self-locking retaining nut · Cirrus Design SR20 and SR22. Effective Nov 8, 2002
- [AD 2001-25-03](https://openairdocs.org/ad/2001-25-03): Rivets In Elevator and Rudder · Cirrus Design SR20 and SR22. Effective Dec 17, 2001
- [AD 2008-06-28](https://openairdocs.org/ad/2008-06-28) (historical): Primary flight display · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 10, 2008
- [AD 2008-06-28 R1](https://openairdocs.org/ad/2008-06-28-R1) (historical): Primary Flight Displays (PFDs) · Avidyne Primary Flight Displays, 441, LC41-550FG and 22 more. Effective Apr 10, 2008
- [AD 2005-17-19](https://openairdocs.org/ad/2005-17-19) (historical): Crew seat recline locks · Cirrus Design SR20 and SR22. Effective Oct 13, 2005
- [AD 2002-05-05](https://openairdocs.org/ad/2002-05-05) (historical): Limitation Section - Cirrus Aircraft Parachute System (CAPS) Activation Cable · Cirrus Design SR20 and SR22. Effective Mar 19, 2002

## Registered aircraft by registry model (OpenAirDocs)

- [Cirrus Design SR22](https://openairdocs.org/model/cirrus-design-sr22): 4,018 aircraft (registry code 2130001)
- [Cirrus Design SR22T](https://openairdocs.org/model/cirrus-design-sr22t): 3,075 aircraft (registry code 2130004)
- [Cirrus Design SR20](https://openairdocs.org/model/cirrus-design-sr20): 1,631 aircraft (registry code 2130000)

## STCs approved under this data sheet (141, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc.
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA12274IB](https://openairdocs.org/stc/SA12274IB): Installation of the MT-Propeller Entwicklung GmbH MTV-9-D/198-52() and MTV-9-D/198-58() propellers. MT-Propeller Entwicklung GmbH
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA12273IB](https://openairdocs.org/stc/SA12273IB): Installation of the MT-Propeller Entwicklung GmbH MTV-9-D/198-52() propeller. MT-Propeller Entwicklung GmbH
- [STC SA12227IB](https://openairdocs.org/stc/SA12227IB): Installation of the MT-Propeller Entwicklung GmbH MTV-9-B/188-50(). MT-Propeller Entwicklung GmbH
- [STC SA02216SE](https://openairdocs.org/stc/SA02216SE): Removal of mechanical link between engine throttle control and propeller RPM control. Installation of a separate RPM control lever, linkage between Cirrus RPM cable/cam followers, center console to accommodate three-lever configuration, new knobs for all levers, and new installation hardware (nuts, bolts, etc). Skyryse Inc.
- [STC SA12064WI](https://openairdocs.org/stc/SA12064WI): Hardware and software updates for the Garmin G1000 Integrated Avionics System. Garmin International Inc.
- [STC SA12084BO](https://openairdocs.org/stc/SA12084BO): Installation of the 700-00212-110 and the 700-00212-010 12-inch Vantage Displays Systems with Attitude Reference System and the 700-00236-000 Air Data Computers System. Avidyne Corporation
- [STC SA12080BO](https://openairdocs.org/stc/SA12080BO): Installation of Prodigy model 90901() LED Landing Light. Whelen Aerospace Technologies
- [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [STC SA12027IB](https://openairdocs.org/stc/SA12027IB): Installation of the MT-Propeller Entwicklung GmbH MTV-14-D/195-30() propeller. MT-Propeller Entwicklung GmbH
- [STC SA02558CH](https://openairdocs.org/stc/SA02558CH): Installation of a L-3 Communications Avionics Systems SmartDeck Flight Guidance and Display System. Acron Aviation Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA02924CH](https://openairdocs.org/stc/SA02924CH): Installation of M-T Propeller model MTV-14-D/195-30( ) 4 bladed propeller.. McFarlane Aviation LLC
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02551AK](https://openairdocs.org/stc/SA02551AK): Installation of SKYDISPLAY Aircraft Interface Device (AID). AeroDisplay LLC
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA10532SC](https://openairdocs.org/stc/SA10532SC): Installation of XM Satellite Radio Wireless equipment.. Heads Up Technologies Inc.
- [STC SA03303CH](https://openairdocs.org/stc/SA03303CH): Installation of MT propeller model MTV-12-D/188-59(). McFarlane Aviation LLC
- [STC SA04575CH](https://openairdocs.org/stc/SA04575CH): Installation of access panel in accordance with Kelly Aerospace Thermal Systems Installation Manual NC-19-092, revision E, or later FAA approved revision.. Kelly Aerospace Thermal Systems LLC
- [STC SA00199BO](https://openairdocs.org/stc/SA00199BO): Installation of Aerox Oxygen System. Aerox Aviation Oxygen Systems LLC
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA01170LA](https://openairdocs.org/stc/SA01170LA): :   Installation of Sandel Avionics SN3308 Navigation Display Unit in accordance with FAA Approved Sandel Avionics Master Drawing List, Document No. ST8691LA-A-01, Revision "B", dated May 14, 2001, or later FAA approved revision.  FAA Approved Airplane Flight Manual Supplement, Document No. ST8691LA-A-09, Revision "N/C", dated June 01, 2001, or later FAA approved revision.. Sandel Avionics LLC
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA01076DE](https://openairdocs.org/stc/SA01076DE): Installation of main battery replacement with Concorde Valve Regulated Lead Acid battery. Concorde Battery Corporation
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA04468CH](https://openairdocs.org/stc/SA04468CH): Installation of Hartzell Propeller model 4C1-F650A1/76C04-0.6 or 4C1-F650A1/76C04B-0.6 i. Hartzell Propeller Inc
- [STC SA02329AK](https://openairdocs.org/stc/SA02329AK): Installation of a fixed-mounted Max-Viz® Enhanced Vision System (EVS) Model 100 or Model 600 to include a sensor with conformal housing that displays imagery on any FAA-approved monitor with NTSC RS-170 video interface capability. PECO Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01234WI-D](https://openairdocs.org/stc/SA01234WI-D): Installation of Bendix/King KMH 880 Multi-Hazard Awareness System or Bendix/King KGP 560 General Aviation Enhanced Ground Proximity Warning System (GA-EGPWS).. Honeywell International Inc
- [STC SA04449CH](https://openairdocs.org/stc/SA04449CH): Retirement life extension of Cirrus Design Corporation aircraft model SR20 in accordance with FAA approved Master Drawing List, E00002953, Revision E, dated February 26, 2020, or later FAA approved revision.. Cirrus Design Corporation
- [STC SA04440CH](https://openairdocs.org/stc/SA04440CH): Installation of Hartzell propeller model 4C1-F650A1/76C04-0.6 or 4C1-F650A1/76C04B-0.6. Hartzell Propeller Inc
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation

All 141: https://openairdocs.org/tcds/A00009CH/stcs.md

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